A solid propellant propulsion system was designed consisting of individual tape-mounted solid propellant rocket motors, which are fed from a storage container into firing position by means of a stepping motor-driven sprocketwheel. The rocket motors are fired, on command, at any of three positions by a signal from an external electrical source. The operation of a typical system in an attitude control application, is shown schematically. Rocket motor optimization studies show that a rectangular motor configuration with an L/D ratio of 2:1 using a simple flat end-burning grain was optimum to provide minimum weight, volume, and sprocket wheel inertia. The design of the rocket motor was based on a quartz-phenolic base, a pre-molded rubber grain inhibitor, a silicone expandable (E) dome, CWP-13 propellant, and a pyrofuze wire pyrotechnic overspray ignition system. The weight of the WSR-101 rocket motor is .0246 pounds.


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    Titel :

    Feasibility Demonstration of a Large Impulse Solid Rocket Attitude Control Motor. Volume 1


    Beteiligte:
    N. J. Rolleri (Autor:in)

    Erscheinungsdatum :

    1966


    Format / Umfang :

    265 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch